副翼-差动平尾组合横滚操纵系统的研究(一)  

THE RESEARCH OF ROLLING CONTROL SYSTEM FOR COMBINED AILERONS AND DIFFERENTIAL TAIL

作　　者：李陆豫 

机构地区：[1]601所

出　　处：《飞行力学》1991年第1期28-34,共7页Flight Dynamics

摘　　要：本文介绍一架双发三角翼常规布局的超音速歼击机,改装应用副翼-差动平尾组合横滚操纵系统的经验和飞行实践.该系统的试飞成功地突破了我国歼击机一直沿用副翼为横向操纵的传统形式,首次应用了气动操纵面的综合利用和组合操纵的新概念。在原机主要结构不更改,仅增重6kg的情况下,使一架较J-7飞机重一倍的歼击机最大滚转速度达到J-7飞机水平.该系统设计中利用了组合操纵的特点,对差动平尾引起的棘手的偏航力矩问题也通过组合方式的巧妙安排,顺利地满足了动态品质的要求.In this paper experience and flight practice applying combined ailerons and differential tail for rolling control system are detailed. The system was modified in a conventional twin-engine powered supersonic fighter wich delta wing. It is the first to use the new concept-the combined aero control surfaces. The success of the system flight test breaks through the traditional way of ailerons for lateral control,which have been used for a long time. At the expense of 5 kg weight increase and no main structure changes, the maximum rolling rate for a fighter heavier than the J-7 by one time is near the same as the J-7. In system design sticky yawing moment due to differential tail was overcome in terms of subtle schedule of combined way, by which dynamic handling quality requirements are well satisfied.

关 键 词：飞机 操纵系统 差动平尾 副翼 

分 类 号：V212.128[航空宇航科学与技术—航空宇航推进理论与工程]